机动载荷对核心机叶尖间隙的影响初探
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摘要
以典型航空发动机核心机为对象,研究模型简化方法,建立完整的计算模型,通过分析机动飞行过程中的主要载荷及作用方式,通过有限元数值模拟,得到机动载荷作用下叶尖径向间隙的变化规律,为研究间隙变化对发动机性能影响提供参考依据。分析发现:陀螺力矩和法向过载均使核心机产生明显的变形,陀螺力矩导致叶尖径向间隙相对变化量的平均值达-2.174,法向过载对叶尖径向间隙变化影响相对较弱,相对变化量的平均值达到-1.572。因此在研究叶尖径向间隙时,不能忽略机动载荷的作用效果。
Based on a typical aircraft engine,the calculation model was built by studying model simplification methods and analyzing main loads and loading procedures in maneuver flight.By grasping the change rule of radial tip clearance subjected to different kinds of maneuvering loads by finite element simulation,it can provide significant reference for studying the effects of tip clearance variation on aero-engine performance.Discovered by rational analysis on the distortion of cases and rotors in consequence of gyroscopic moment and normal overload,it can be concluded that two kinds of loads can cause distinct deformation in the coreengine.The mean of the relative variation of radial tip clearance subjected to gyro moment was up to-2.174,while the value subjected to normal overload was up to-1.572 owing to the weaker influence of normal overload.Consequently,the impacts of maneuvering loads on engines cannot be ignored when studying the radial tip clearance variation.
Based on a typical aircraft engine,the calculation model was built by studying model simplification methods and analyzing main loads and loading procedures in maneuver flight.By grasping the change rule of radial tip clearance subjected to different kinds of maneuvering loads by finite element simulation,it can provide significant reference for studying the effects of tip clearance variation on aero-engine performance.Discovered by rational analysis on the distortion of cases and rotors in consequence of gyroscopic moment and normal overload,it can be concluded that two kinds of loads can cause distinct deformation in the coreengine.The mean of the relative variation of radial tip clearance subjected to gyro moment was up to-2.174,while the value subjected to normal overload was up to-1.572 owing to the weaker influence of normal overload.Consequently,the impacts of maneuvering loads on engines cannot be ignored when studying the radial tip clearance variation.
引文
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[15]富贵华.稳定俯仰机动飞行包线研究及最大机动载荷的计算[J].中国民航学院学报,1985(2):9-18.FU Guihua.Research on stabilizing pitch maneuvering flight envelope and calculation of maximum maneuvering load[J].Journal of Civil Aviation University of China,1985(2):9-18.(in Chinese)
[16]薛园园.基于核心机的高压涡轮叶尖径向间隙分析技术研究[D].北京:北京航空航天大学,2017.XUE Yuanyuan.Turbine radial tip clearance analysis based on core-engine model[D].Beijing:Beijing University of Aeronautics and Astronautics,2017.(in Chinese)
[17]王超,王延荣,徐星仲,等.应用三维有限元法计算汽轮机转子临界转速和模化长叶片[J].动力工程,2007,27(6):840-844.WANG Chao,WANG Yanrong,XU Zhongxing,et al.Simulation of long blades and calculation of critical speeds of the steam turbine rotor by 3Dfinite element methods[J].Journal of Power Engineering,2007,27(6):840-844.(in Chinese)
[18]胡延青.航空发动机叶尖径向间隙研究进展综述[J].航空发动机,2014,40(1):60-67.HU Yanqing.Overview on aeroengine radial tip clearance[J].Aeroengine,2014,40(1):60-67.(in Chinese)
[2]郭淑芬,徐波.涡轮叶尖径向主动间隙控制研究[J].航空发动机,2000(2):47-51.GUO Shufen,XU Bo.Research on radial active clearance control of turbine blade[J].Aeroengine,2000(2):47-51.(in Chinese)
[3]SHAWN C T,BRUCE M S,JAY J O.Further characterization of an active clearance control concept[R].AIAA-2007-5379,2007.
[4]熊宇飞.航空发动机转子叶尖间隙测量[J].测控技术,2004,23(1):5-7.XIONG Yufei.Rotor tip-clearance measurement in aeroengine[J].Measurement and Control Technology,2004,23(1):5-7.(in Chinese)
[5]航空航天工业部《高效节能发动机文集》编委会.高效节能发动机文集:第5分册涡轮设计和试验[M].北京:航空工业出版社,1991.
[6]OLSSON W J,MARTIN R L.B747/JT9Dflight loads and their effect on the engine running clearance and performance deterioration BCAC NAL10and WA JT9Dengine diagnostics programs[R].NASA-CR-165573,1982.
[7]邱立新,王振华.航空发动机叶尖间隙测量研究[J].航空发动机,2001(4):26-29.QIU Lixin,WANG Zhenhua.Research on aero-engine tip clearance measurement[J].Aeroengine,2001(4):26-29.(in Chinese)
[8]徐有方.航空燃气涡轮发动机压气机径向间隙计时图的计算方法[J].燃气轮机技术,1989,3(9):40-43.Calculation method of radial gap timing chart for aviation gas turbine engine compressor[J].Gas Turbine Technology,1989,3(9):40-43.(in Chinese)
[9]贾炳辉,张小栋,彭凯.机动飞行下的涡轮叶尖间隙动态变化规律[J].航空动力学报,2011,26(12):2757-2764.JIA Binghui,ZHANG Xiaodong,PENG Kai.Dynamic changes rule of aero-engine turbine tip clearance in maneuver flight[J].Journal of Aerospace Power,2011,26(12):2757-2764.(in Chinese)
[10]牛冬生.涡轮叶尖间隙数值分析和冷热态尺寸换算方法研究[D].南京:南京航空航天大学,2004.NIU Dongsheng.Research on numerical analysis of turbine blade tip clearance and conversion of cold and hot dimensions[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2004.(in Chinese)
[11]BENITO D,DIXON J,METHERELL P.3Dthermo-mechanical modelling method to predict compressor[R].ASME Paper GT2008-50780,2008.
[12]祝长生,陈拥军.机动飞行时发动机转子系统动力学统一模型[J].航空动力学报,2009,24(2):371-377.ZHU Changsheng,CHEN Yongjun.General dynamic model of aeroengine's rotor system during maneuvering flight[J].Journal of Aerospace Power,2009,24(2):371-377.(in Chinese)
[13]王通北,陈美英.谈国军标GJB241-87中的外部作用力和陀螺力矩[J].航空发动机,1998(2):25-31,15.WANG Tongbei,CHEN Meiying.Discussion about external force and gyro torque in national military standard GJB241-87[J].Aeroengine,1998(2):25-31,15.(in Chinese)
[14]谢传锋,王琪.理论力学[M].北京:高等教育出版社,2009.
[15]富贵华.稳定俯仰机动飞行包线研究及最大机动载荷的计算[J].中国民航学院学报,1985(2):9-18.FU Guihua.Research on stabilizing pitch maneuvering flight envelope and calculation of maximum maneuvering load[J].Journal of Civil Aviation University of China,1985(2):9-18.(in Chinese)
[16]薛园园.基于核心机的高压涡轮叶尖径向间隙分析技术研究[D].北京:北京航空航天大学,2017.XUE Yuanyuan.Turbine radial tip clearance analysis based on core-engine model[D].Beijing:Beijing University of Aeronautics and Astronautics,2017.(in Chinese)
[17]王超,王延荣,徐星仲,等.应用三维有限元法计算汽轮机转子临界转速和模化长叶片[J].动力工程,2007,27(6):840-844.WANG Chao,WANG Yanrong,XU Zhongxing,et al.Simulation of long blades and calculation of critical speeds of the steam turbine rotor by 3Dfinite element methods[J].Journal of Power Engineering,2007,27(6):840-844.(in Chinese)
[18]胡延青.航空发动机叶尖径向间隙研究进展综述[J].航空发动机,2014,40(1):60-67.HU Yanqing.Overview on aeroengine radial tip clearance[J].Aeroengine,2014,40(1):60-67.(in Chinese)